Abstract: An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).

Abstract: An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

Abstract: An aircraft nacelle includes an air intake (40) that makes it possible to channel a stream of air (42) in the direction of a power plant (44), whereby the air intake (40) includes an inside pipe (48) that forms an aerodynamic surface (52) that is in contact with the stream of air (42) that is extended toward the rear by an aerodynamic surface (54) of a pipe (56) of the power plant, characterized in that it includes a support (66) of at least one measuring device (68), whereby the support (66), in annular form, is able to be inserted in a removable way between the air intake (40) and the power plant (44) and includes a so-called aerodynamic surface (70) that can ensure the continuity of the aerodynamic surfaces (52, 54) that are arranged downstream and upstream according to the direction of flow of the stream of air (42).

Abstract: An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer (50) between which are arranged at least one alveolar structure (52) with a number of cells dedicated to the acoustic treatment, and de-icing cavities (58) in which hot air circulates in contact with the acoustically resistive layer to ensure a frost treatment, characterized in that it includes holes for supplying de-icing cavities (58) with hot air and in that the capacity to treat the frost is adjusted along the zones by modifying the open surface ratio that results from the holes.

Abstract: An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface.

Abstract: According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A).

Abstract: A propulsion unit includes at least one exhaust pipe (62, 76) that includes an air discharge that is delimited by a trailing edge (78, 82). The end part of the exhaust pipe (62, 76) includes two scalloped shapes (84) that each correspond to a preferred acoustic radiation direction, separated by advanced parts (86) that can limit the acoustic radiation, whereby the scalloped shapes are offset upward relative to the horizontal median plane.

Abstract: According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.